Engine inlet protective screen arrangement



Jan. 17, 1967 SHAO-TANG LEE 3,298,637

ENGINE INLET PROTECTIVE SCREEN ARRANGEMENT Original Filed June 15, 19642 Sheets-Sheet 1.

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INVEN'I'OR BY 1.! Mai E 1957 $HAO-TANG LEE 3,298,637

ENGINE INLET PROTECTIVE SCREEN ARRANGEMENT Original Filed June 15, 19642 Sheets-Sheet 2 Shaa -Tang Lee INVENTORU 13y QM United States Patent G3,298,637 ENGINE INLET PROTECTIVE SCREEN ARRANGEMENT Shae-Tang Lee, 25Chi-kuang St., Taichung, Taiwan, China Original application June 15,1964, Ser. No. 375,391. Di-

vided and this application Sept. 22, 1965, Ser. No. 489,125

12 Claims. (Cl. 244-53) This application is a division of applicationSerial No. 375,391, filed June 15, 1964, which is in turn acontinuation-in-part of application Serial No. 219,652, filed August 27,1962, now Patent No. 3,165,280. The invention set forth herein generallyrelates to jet engines, and is more particularly concerned with meansfor providing a protective barrier at the intake end thereof.

It is a primary object of the instant invention to provide means forselectively establishing a temporary barrier at the inlet end of a jetengine so as to exclude, to a large degree, the entry of foreign mattersuch as water or dust.

In conjunction with the above object, it is also an object of theinstant invention to utilize a fluid, and more specifically gas or air,barrier, either alone or in conjunction with selectively closableshutter blades, so as to provide the protective means for the jet intakeend.

Further, it is an object of the instant invention to provide meanswhereby a protective screen or barrier can be formed about the intakeend of a jet engine without requiring an actual closing of the end in amanner which would shut off the normal supply of air.

Basically, in achieving the above objects, it is contemplated that aconventional jet engine be modified about the intake end thereof so asto include an encircling enlarged hollow conduit having a continuousseries of discharge holes therein, this series of holes being eitherdirected inwardly or outwardly relative to the intake end whereby, uponthe discharge of pressurized air therethrough, an air or fluid screen isprovided so as to effectively exclude any dust and/ or water which mightbe splashed up by the thrust of the engine when, for example, taking offvertically from soft ground or water. In ad dition, it is contemplatedthat the engine also be provided with a series of selectively closableshutter blades for effecting a further closing of the intake end. Such ashutter, depending upon the particular condition under which theaircraft is to be used, would be optional in those engines wherein thefluid barrier is formed outwardly of the intake end as compared to thoseengines wherein the fluid barrier is formed directly over the intakeend.

These together with other objects and advantages which will becomesubsequently apparent reside in the details of construction andoperation as more fully hereinafter described and claimed, referencebeing had to the accompanying drawings forming a part hereof, whereinlike numerals refer to like parts throughout, and in which:

FIGURE 1 is a schematic side view of an aircraft illustrating rotatablymounted jet engines;

FIGURE 2 is an enlarged side view of the forward or intake portion of ajet engine having the features of the instant invention incorporatedtherein, portions of this view being broken away for purposes ofillustration;

FIGURE 3 is a transverse view of the head of the jet illustrating theshutter in its open position and one arrangement of air dischargeapertures or holes;

FIGURE 4 is a view similar to FIGURE 3 illustrating the shutter in itsclosed position;

FIGURE 5 is a view similar to FIGURE 2 with the shutter constructionremoved and illustrating a modified arrangement of air discharge holes;

FIGURE 6 is a partial detail view illustrating an outwardly and upwardlydirected arrangement of the air discharge holes;

FIGURE 7 is a view similar to FIGURE 6 illustrating an outwardly anddownwardly directed arrangement of the discharge holes;

FIGURE 8 is a schematic view illustrating the fluid barrier formedutilizing the hole arrangement shown in FIGURE 7;-

FIGURE 9 is a schematic view illustrating the fluid barrier formed bythe hole arrangement shown in FIG- URE 6; and

FIGURE 10 is a schematic view illustrating the fluid barrier achieved byutilizing the hole arrangement shown in FIGURES 2-4.

Referring now more specifically to the drawings, reference numeral 10 isused to generally designate a jet engine having the improvements of theinstant invention incorporated therein. The jet engine 10 will normallybe rotatably mounted on an aircraft 12 in any conventional manner so asto enable a vertical taking off of the aircraft in that the specificinventive features involved herein find particular, although notexclusive utility under vertical take-ofl conditions.

The jet engine .10, referring specifically to FIGURES 2-4, is providedat its intake or forward end with both a selectively closable shutter 14and means for providing a fluid, and more particularly gas or air,barrier. These features are particularly useful as a means forexcluding, from the engine 10, any dust and/ or water which might besplashed up by the thrust of the jet when vertically taking off fromsoft ground or water. Inasmuch as the closing of the shutter 14 and theforming of the air barrier will effectively close off the intake end ofthe engine 10, it is contemplated that liquid air be introduced theretoin a conventional manner from any conventional source. Incidentally,this introduction of liquid air is in itself desirable inasmuch as thesupply of air generally provided from the gliding movement of the planeduring a conventional horizontal take-01f is not available in a verticaltake-off.

With particular reference to the shutter 14, it will be noted that aplurality of overlapping arcuate flat thin blades 16 are provided, each,piv otally mounted, inward of the outer end thereof, to a rigidradially inwardly extending projection 18, this point of engagementbeing indicated by reference numeral 20. A first flexible cable 22 isfixed to each blade 16 forward of the pivot point 20, and a secondflexible cable 24 is fixed to each shutter blade 16 rearward of thepivot point 20. Both of these cables 22 and 24 extend through aperturesin the engine housing, and have the outer ends thereof fixedly locked toa ring 26 slidable about the exterior of the engine housing within guiderings or loops 28. The pair of cables 22 and 24 associated with each ofthe blades 16 are of a length whereby rotation of the control ring 26 inone direction will effect an opening pivotal movement of the shutterblades 16, while a rotational movement of the control ring 26 in theopposite direction will effect a pivotal movement of the shutter blades16 in the opposite direction to a closed position.

The blades 16 are normally maintained in their open position through thebiasing force of a compression coil spring 30 which is engaged between afixed abutment 32 on the ring 26 and a second abutment 34 fixed to themotor housing. In order to effect the closing of the shutter 14, anelongated control cable 36 is provided, this control cable being fixedto an arcuate guide rod 38 which is in turn slidably received through amounting lug 40, the fixed abutment 34, and the coil spring 30, and issecured, at the end thereof, to the ring abutment 32 whereby a pull onthe control cable 36 will effect a movement of the ring 26 so as toproduce a closing of the shutter 14. Upon release of the control cable36, it will be appreciated that the spring 30 will effect an automaticopening of the shutter 14 through an outward pivoting of the shutterblades 16.

The particular fluid barrier or air tent used in this form of theinvention is contemplated to completely close off the intake end of thejet motor 10 forward of the shutter 14 which is actually located inwardof the extreme forward end of the motor 10. In order to achieve thedesired air tent, which has incidently been schematically illustrated inFIGURE 10 and indicated by reference numeral 42, a circular hollowconduit or air chamber 44 is defined at the intake end of the jet engine10. The conduit 44 is communicated with any suitable source ofpressurized air or gas through the pipe 46. The discharge of air fromthe conduit 44 is through a series of inwardly and forwardly directedholes or apertures 48 completely thereabout. These holes 48 are directedradially inward and slightly forward of the intake end so as to providefor a meeting of the pressurized air streams, discharged therethrough ata generally central point, thereby forming a tent or barrier 42 over theintake end. Thus, the barrier 42 either in itself or in conjunction withthe shutter 14 forms a means for ex eluding foreign matter from theengine.

In actual use, when a plane 12 is to take off under conditions wherebyit is conceivable that foreign matter, such as dirt or water, will bedrawn into the jet engines, the shutter 14 is closed, a gas barrier isformed through the discharge apertures 48 forward of the shutter 14, andliquid air is fed to the engines until a predetermined height isachieved. At this point, the shutters are opened and the gas barrier iscut off so as to enable the jet engine It to function in the normalmanner.

With reference to FIGURES 9, it will be appreciated that the air barrierforming means has been modified I slightly in that the air dischargeapertures 50 are directed, substantially radially, outward about theintake end of the jet engine 10. These holes 50 can either be forwardlyand upwardly inclined as illustrated in FIGURE 6 so as to form abowl-shaped barrier 52, noting FIGURE 9, or slightly downwardly directedas in FIGURE 7 so as to form a collar-shaped barrier 54, noting FIGURE8. In each instance, it is contemplated that sufiicient holes 50 beprovided and a sufiicient pressure be utilized so as to form asubstantially solid barrier about the intake end of the engine ltl so asto effectively restrain or block any dust or water which would tend tobe thrown up by the engine during the take-01f phase thereof.Incidentally, inasmuch as the barriers 52 and 54 are actually formedoutward of the engine 10, the shutter 14 need not be provided inconjunction therewith, thereby not cutting off the regular air supply tothe engine 10 and consequently avoiding the need for artificiallyproviding such air such as in the nature of liquid air.

From the foregoing, it should be appreciated that a highly novel meanshas been provided for selectively producing a barrier at the intake endof a jet engine so as to exclude the introduction of foreign matter intothe engine at the take-off stage. As detailed supra, this is basicallyachieved through the provision of an air seal or screen either directlyover the intake end of the engine or radially outward andcircumferentially about the intake end of the engine, with the airbarriers so formed being supplemented, as desired, by a selectivelyclosable shutter mounted within the intake end.

The foregoing is considered as illustrative only of the principles ofthe invention. Further, since numerous modifications and changes willreadily occur to those skilled in the art, it is not desired to limitthe invention to the exact construction and operation shown anddescribed, and accordingly all suitable modifications and 4 equivalentsmay be resorted to, falling within of the invention as claimed.

What is claimed as new is as follows:

1. For particular use as a jet engine adapted for vertical dispositionin a VTOL aircraft, a jet engine comprising a forward intake end, a rearexhaust end, and means for selectively forming a fluid barriercircumferentially about the intake end so as to exclude foreign mattertherefrom.

2. The construction of claim 1 wherein said means includes a hollowconduit surrounding said intake end, an inlet line for pressurized fluidcommunicated with said conduit for the introduction of pressurized fluidthereto, and a plurality of fluid discharge apertures in said conduit atgenerally equally spaced points completely about said intake end, saidapertures being directed generally laterally of the intake end of theengine whereby fluid discharged therethrough will form a substantiallycircular fluid barrier about the intake end.

3. The construction of claim 2 wherein said apertures are directedgenerally radially outward peripherally about said intake end, so as toform an outwardly extending fluid collar thereabout.

4. The construction of claim 1 including selectively operable shuttermeans mounted within the intake end of said engine inward of the fluidbarrier forming means for closing said intake end, and auxiliary airsupply means for supplying air to said engine when said shutter means isclosed.

5. The construction of claim 2 wherein said apertures are directedgenerally radially inward across said intake end so as to form a fluidcover thereover, selectively operable shutter means mounted within theintake end of said engine inward of the fluid barrier forming means forclosing said intake end, and auxiliary air supply means for supplyingair to said engine when said shutter means is closed.

6. The construction of claim 3 wherein said outwardly directed aperturesare angled slightly rearward relative to said intake end and toward saidexhaust end.

7. The construction of claim 3 wherein said outwardly directed aperturesare angled slightly forward relative to said intake end.

8. The construction of claim 4 wherein said engine includes a hollowcylindrical body, said shutter means comprising a plurality ofoverlapped generally coplanar elongated blades, means mounting saidblades on the interior of said body for movement from a first positionlying adjacent the interior surface of said body completely thereaboutand defining an enlarged central opening, and a second positionprojecting generally radially inward from said body and closing saidopening, and means for selectively and simultaneously moving saidblades.

9. The construction of claim 8 wherein the means mounting said bladescomprises a plurality of inwardly extending radial projections fixed tosaid body, and pivot means fixing each blade, inward of one end thereof,to a different projection, said means for moving said blades comprisinga movable control mounted on said engine, means engaged between eachblade, outward of the pivot means, and the control whereby movementofsaid control in one direction effects an inward swinging of said thescope blades, and means engaged between each blade, inward of the pivotmeans, and the control whereby movement of said control in one directioneffects an outward swinging of said blades.

10. A jet engine comprising a hollow cylindrical body, a forward intakeend, a rear exhaust end, and selectively operable shutter means mountedwithin said body adjacent said intake end, said shutter means comprisinga plurality of overlapped generally coplanar elongated blades, meansmounting said blades on the interior of said body for movement from afirst position lying adjacent the interior surface of said bodycompletely thereabout and defining an enlarged central opening, and asecond position projecting generally radially inward from said body andclosing said opening, means for selectively and simultaneously movingsaid blades, and auxiliary air supply means for supplying air to saidengine when said opening is closed.

11. The construction of claim 10 wherein the means mounting said bladescomprises a plurality of inwardly extending radial projections fixed tosaid body, and pivot means fixing each blade, inward of one end thereof,to a different projection, said means for moving said blades comprisinga movable control ring mounted on said engine, means engaged betweeneach blade, outward of the pivot means, and the control ring wherebymovement of said control ring in one direction effects an inwardswinging of said blades, and means engaged between each blade, inward ofthe pivot means, and the control ring whereby movement of said controlring in one direction efiects an outward swinging of said blades.

12. A vertically positionable jet engine comprising an upwardlydirectable intake end, a downwardly directable exhaust end, a conduitsurrounding said intake end, an inlet line for pressurized fluidcommunicated with said conduit for the introduction of pressurized fluidthereto, and a plurality of fluid discharge apertures in said conduit atgenerally equally spaced points completely about said intake end, saidapertures being directed generally laterally of the intake end of theengine whereby fluid discharged therethrough will form a substantiallycircular fluid barrier about the intake end.

References Cited by the Examiner UNITED STATES PATENTS 2,915,262 12/1959 Klein 24474 3,168,999 2/1965 Warren et al 24453 MILTON BUCHLER,Primary Examiner.

LARRY C. HALL, B. BELKIN, Examiners.

1. FOR PARTICULAR USE AS A JET ENGINE ADAPTED FOR VERTICAL DISPOSITIONIN A VTOL AIRCRAFT, A JET ENGINE COMPRISING A FORWARD INTAKE END, A REAREXHAUST END, AND MEANS FOR